US5934614A - Closed loop control system for controlling an air discharge out of an aircraft body - Google Patents
Closed loop control system for controlling an air discharge out of an aircraft body Download PDFInfo
- Publication number
- US5934614A US5934614A US08/891,519 US89151997A US5934614A US 5934614 A US5934614 A US 5934614A US 89151997 A US89151997 A US 89151997A US 5934614 A US5934614 A US 5934614A
- Authority
- US
- United States
- Prior art keywords
- controllers
- conductor
- closed loop
- control system
- interfaces
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D13/00—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft
- B64D13/02—Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space, or structural parts of the aircraft the air being pressurised
- B64D13/04—Automatic control of pressure
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Definitions
- the invention relates to controlling the discharge of used-up air out of an enclosed space, particularly an aircraft body. Redundant control paths must be provided to assure or at least increase the probability of a proper operation even when there are faults in the system.
- outflow valves for controlling the volume of used air to be discharged out of a passenger aircraft body are controlled by closed loop controllers through unidirectional databuses.
- Each closed loop controller supplies a control signal or valve adjustment value through a separate databus to the respective outflow valve or valves.
- These valves are distributed along the length of the aircraft body and provide an air passage from the inside of the aircraft body to the atmosphere. In response to such a control the valves discharge regulated volumes of used air to the atmosphere.
- a further feedback databus is provided for each valve to provide feedback information regarding the current status of the respective valve to the closed loop controller.
- Such a conventional system requires a total of eight databuses for each valve in the system.
- Four of one-way databuses connect two master controllers to two slave valve controllers and four one-way return databuses connect the slave valve controllers with master controllers, for supplying feedback information to the master controllers.
- the conventional systems are not constructed to increase the reliability of the system.
- each master controller can control only the outflow or air discharge valve to the slave controllers of which it is connected. Intercommunication between any master controller and any one of a plurality of slave valve controllers is conventionally not possible.
- Another drawback of such conventional systems is seen in that a two-way intercommunication between all components of the system is either not possible at all or at least economically not feasible.
- the system shall be economical, yet sufficiently reliable to meet official aircraft construction standards;
- the system must be able to respond to currently prevailing operating conditions in the aircraft especially the pressure within the aircraft cab in;
- a closed loop control system for controlling an air discharge from an aircraft body having a body wall through which at least one air outflow valve extends.
- the present closed loop control system in its simplest construction with but one valve is characterized in that the valve is controllable by any one of two slave valve controllers which in turn are controllable by any one of two master controllers.
- the slave controllers and the master controllers a re interconnected by a signal or information transmission loop for transmitting control information from the master controllers to the slave controllers and for transmitting feedback or other information for example representing the current cabin pressure, from the slave valve controllers and other system components such as air pressure gages, to the master controllers so that each of the master controllers can control any one of the slave controllers and so that return information can reach any one of the master controllers.
- Such a system has the advantage that it can be easily extended to virtually any number of valves, whereby the respective signal and information transmission loop is extended by additional conductor sections sufficient to provide the described interconnection between any master controller and any slave controller of the system while simultaneously satisfying the redundancy required by aircraft manufacturing regulations.
- the information transmission loop can be provided with an intermeshed conductor system through the simple device of conductor junction boxes or fiber optical couplers depending on whether insulated electrical conductor wires or optical lightwave conductors are used. In both instances virtually any number of parallel and series connected conductor sections may be used to form an intermeshed loop conductor system.
- FIG. 1 shows an arrangement with one air outflow valve responsive to two slave valve controllers which in turn are connected through the present transmission loop to two master controllers;
- FIG. 2 shows a block diagram similar to that of FIG. 1, however illustrating an expanded system with N-number of valves each having two slave controllers and two master controllers interconnected by an intermeshed conductor loop.
- FIG. 1 shows an embodiment with one air discharge valve V which is controllable by two master controllers 1 and 2 controlling in turn two slave valve controllers 1D and 2D.
- the master controllers 1 and 2 that may be combined to form a unit 4 shown in FIG. 2, are connected to the slave controllers 1D and 2D through a conductor loop 3 and loop entering and exiting conductor sections. More specifically, the master controller 1 which is equipped with a logic signal or information evaluating circuit 1A is connected to the loop 3 by a column conductor section 1B at an interface 3A. The loop 3 in turn is connected to the slave controller 1D by a column conductor section 1C at an interface 3D.
- the master controller 2 also equipped with a logic signal or information evaluating circuit 2A is connected to the loop 3 by a column conductor section 2B at an interface 3B.
- the loop in turn is connected by a column conductor section 2C to the slave controller 2D at an interface 3C.
- the loop is formed by the above mentioned interfaces 3A, 3B, 3C and 3D forming junctions which are interconnected by conductor sections as follows.
- the interface or junction 3A is connected to the junction or interface 3B by a row conductor section 3F.
- the interface or junction 3D is connected to the junction or interface 3C by a row connector section 3H.
- the junction or interface 3B is connected to the junction or interface 3C by a column conductor section 3G.
- the junction or interface 3A is connected by a column conductor 3E to the junction or interface 3D.
- the circular conductor loop 3 is formed.
- the interfaces or junctions are, for example, junction boxes where the conductor sections are insulated electrical wires or conductors or these junctions are optical fiber couplers where the conductor sections are lightwave conductors.
- the arrow heads at each end of the conductor sections indicate that the conductors can transmit signals in either direction.
- valve V Under a normal operating condition the valve V is operated by the master controller 1 through the following shortest conductor path: master controller 1, logic circuit 1A, conductor section 1B, junction 3A, conductor section 3E, junction 3D, conductor section 1C, slave valve controller 1D.
- the shortest possible conductor path will again be established as follows: 2, 2A, 2B, 3B, 3G, 3C, 2C, 2D. If the controller 2 and the conductor 3E do not work the control can still be accomplished, for example along: 1B, 3A, 3F, 3B, 3G, 3C, 2C.
- FIG. 2 illustrates an embodiment in which a plurality of master control units 1, 2, . . . , N-1, and N form control units 4 which are connected to slave valve control units 5 also arranged in pairs so that each valve V1 to VN has two slave valve controllers as described above with reference to FIG. 1.
- the loop is constructed as an interlinked loop 3' wherein a circular or rather an endless loop includes additional conductor sections arranged in rows RCS and columns CCS with further junctions JP to accommodate a larger number of master control units 4 and a correspondingly larger number of controlled or slave controller units 5.
- the loop 3' has, for example eight major junctions 3.1, 3.2, 3.3, 3.4, 3.5, 3.6, 3.7, 3.8 and a number of secondary junctions 3.9 and 3.10 interconnected in an endless loop by conductor sections 3.11, 3.12, 3.13, 3.14, 3.15, 3.16, 3.17, 3.18, 3.19, and 3.20
- additional junctions may be provided at the crossing or junction points JP between the row conductor sections RCS and column conductor sections CCS.
- the conductor sections 1B, 2B, N-1B and NB, as well as the conductor sections 1C, 2C, N-1C and NC form part of column conductor links and are simultaneously entrance and exit conductor sections for the endless conductor loop 3'.
- the logic signal evaluation circuits 1A, 2A, . . . , N-1A, NA assure that under normal operating conditions and under emergency operating conditions always the shortest interconnection is established. Moreover, the logic circuits make sure that any of the master controllers can control any one of the slave valve controllers, whereby again the shortest available communication link has preference over any longer possible communication link. The logic circuits also assure that any available master controller will control any available slave valve controller for safely operating the respective valve under all operating conditions. If one valve is inoperable for whatever reason, any of the other valves can be operated for the intended purpose of discharging used air from an aircraft body.
Abstract
Description
Claims (12)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19628395A DE19628395C2 (en) | 1996-07-13 | 1996-07-13 | System for controlling the exhaust air volume flows of an aircraft |
DE19628395 | 1996-07-13 |
Publications (1)
Publication Number | Publication Date |
---|---|
US5934614A true US5934614A (en) | 1999-08-10 |
Family
ID=7799818
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US08/891,519 Expired - Lifetime US5934614A (en) | 1996-07-13 | 1997-07-11 | Closed loop control system for controlling an air discharge out of an aircraft body |
Country Status (3)
Country | Link |
---|---|
US (1) | US5934614A (en) |
EP (1) | EP0818388B1 (en) |
DE (2) | DE19628395C2 (en) |
Cited By (17)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1209079A1 (en) * | 2000-11-28 | 2002-05-29 | Nord-Micro AG & Co. OHG | Cabin pressure control system, method of controlling the actual pressure inside a cabin and outflow valve |
US6737988B2 (en) | 2002-02-21 | 2004-05-18 | Honeywell International, Inc. | Instrumentation and control circuit having multiple, dissimilar sources for supplying warnings, indications, and controls and an integrated cabin pressure control system valve incorporating the same |
US20040139751A1 (en) * | 2003-01-22 | 2004-07-22 | Liu Guang Jun | Master-slave engine bleed flow sharing control method and system |
US20060174628A1 (en) * | 2005-02-09 | 2006-08-10 | Honeywell International Inc. | Method and system for balancing bleed flows from gas turbine engines |
GB2443964A (en) * | 2006-11-17 | 2008-05-21 | Boeing Co | An environmental control system for controlling the environment in a pressurised compartment |
US7586888B2 (en) | 2005-02-17 | 2009-09-08 | Mobitrum Corporation | Method and system for mesh network embedded devices |
US7630736B2 (en) | 2005-10-11 | 2009-12-08 | Mobitrum Corporation | Method and system for spatial data input, manipulation and distribution via an adaptive wireless transceiver |
US20090305622A1 (en) * | 2006-01-12 | 2009-12-10 | Airbus Deutschland Gmbh | Process and system for controlling the pressure in an aircraft cabin |
US20100173575A1 (en) * | 2009-01-08 | 2010-07-08 | Darrell Horner | Multiple outflow valve cabin pressure control system |
US20100233950A1 (en) * | 2009-03-10 | 2010-09-16 | Honeywell International Inc. | Aneroid replacement |
US7801058B2 (en) | 2006-07-27 | 2010-09-21 | Mobitrum Corporation | Method and system for dynamic information exchange on mesh network devices |
US20120003908A1 (en) * | 2008-11-21 | 2012-01-05 | Airbus Operations Gmbh | Method And System For Emergency Ventilation Of An Aircraft Cabin In The Case Of A Leak In The Area Of An Air Mixer |
US8305936B2 (en) | 2006-07-27 | 2012-11-06 | Mobitrum Corporation | Method and system for dynamic information exchange on a mesh network in a vehicle |
US8305935B2 (en) | 2006-07-27 | 2012-11-06 | Mobitrum Corporation | Method and system for dynamic information exchange on location aware mesh network devices |
US8411590B2 (en) | 2006-07-27 | 2013-04-02 | Mobitrum Corporation | Mesh network remote control device |
US8427979B1 (en) | 2006-07-27 | 2013-04-23 | Mobitrum Corporation | Method and system for dynamic information exchange on location aware mesh network devices |
USRE47894E1 (en) | 2006-07-27 | 2020-03-03 | Iii Holdings 2, Llc | Method and system for dynamic information exchange on location aware mesh network devices |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3679156A (en) * | 1970-07-20 | 1972-07-25 | Ltv Electrosystems Inc | Fly-by-wire |
US3740006A (en) * | 1971-07-29 | 1973-06-19 | Aircraft Corp | Aircraft cabin outflow valve with torque reduction and noise abatement means |
US4436018A (en) * | 1981-02-17 | 1984-03-13 | Textron Inc. | Multiple loop control system |
US4651045A (en) * | 1985-04-26 | 1987-03-17 | Messerschmitt-Bolkow-Blohm Gmbh | Electromagnetically interference-proof flight control device |
US4807516A (en) * | 1987-04-23 | 1989-02-28 | The Boeing Company | Flight control system employing three controllers operating a dual actuator |
US5001638A (en) * | 1989-04-18 | 1991-03-19 | The Boeing Company | Integrated aircraft air data system |
US5046686A (en) * | 1988-04-18 | 1991-09-10 | Abg-Semca | Clack valve and flap valve with a controlled valve as well as aircraft with controlled valve of this type |
US5274554A (en) * | 1991-02-01 | 1993-12-28 | The Boeing Company | Multiple-voting fault detection system for flight critical actuation control systems |
US5273486A (en) * | 1992-11-27 | 1993-12-28 | United Technologies Corporation | Adaptive aircraft cabin pressure control system |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4164896A (en) * | 1977-06-13 | 1979-08-21 | The Garrett Corporation | Control alternating system |
FR2630183B1 (en) * | 1988-04-18 | 1990-09-07 | Abg Semca | VALVE WITH AUTOMATIC OPENING AND AIRCRAFT COMPRISING SUCH A VALVE |
FR2632044B1 (en) * | 1988-05-27 | 1990-12-14 | Abg Semca | VALVE WITH AUTONOMOUS OPENING AND AIRCRAFT COMPRISING SUCH A VALVE |
US5297987A (en) * | 1992-06-01 | 1994-03-29 | United Technologies Corporation | Pressure control servo loop |
DE4316886C2 (en) * | 1993-05-19 | 1995-05-18 | Nord Micro Elektronik Feinmech | Cabin pressure control system for aircraft |
-
1996
- 1996-07-13 DE DE19628395A patent/DE19628395C2/en not_active Expired - Fee Related
-
1997
- 1997-06-23 DE DE59704642T patent/DE59704642D1/en not_active Expired - Lifetime
- 1997-06-23 EP EP97110252A patent/EP0818388B1/en not_active Expired - Lifetime
- 1997-07-11 US US08/891,519 patent/US5934614A/en not_active Expired - Lifetime
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3679156A (en) * | 1970-07-20 | 1972-07-25 | Ltv Electrosystems Inc | Fly-by-wire |
US3740006A (en) * | 1971-07-29 | 1973-06-19 | Aircraft Corp | Aircraft cabin outflow valve with torque reduction and noise abatement means |
US4436018A (en) * | 1981-02-17 | 1984-03-13 | Textron Inc. | Multiple loop control system |
US4651045A (en) * | 1985-04-26 | 1987-03-17 | Messerschmitt-Bolkow-Blohm Gmbh | Electromagnetically interference-proof flight control device |
US4807516A (en) * | 1987-04-23 | 1989-02-28 | The Boeing Company | Flight control system employing three controllers operating a dual actuator |
US5046686A (en) * | 1988-04-18 | 1991-09-10 | Abg-Semca | Clack valve and flap valve with a controlled valve as well as aircraft with controlled valve of this type |
US5001638A (en) * | 1989-04-18 | 1991-03-19 | The Boeing Company | Integrated aircraft air data system |
US5274554A (en) * | 1991-02-01 | 1993-12-28 | The Boeing Company | Multiple-voting fault detection system for flight critical actuation control systems |
US5273486A (en) * | 1992-11-27 | 1993-12-28 | United Technologies Corporation | Adaptive aircraft cabin pressure control system |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2002044023A1 (en) * | 2000-11-28 | 2002-06-06 | Nord-Micro Ag & Co. Ohg | Cabin pressure control system, method of controlling the actual pressure inside a cabin and outflow valve |
US6746322B2 (en) * | 2000-11-28 | 2004-06-08 | Nord-Micro Ag & Co. Ohg | Cabin pressure control system, method of controlling the actual pressure inside a cabin and outflow valve |
EP1209079A1 (en) * | 2000-11-28 | 2002-05-29 | Nord-Micro AG & Co. OHG | Cabin pressure control system, method of controlling the actual pressure inside a cabin and outflow valve |
US6737988B2 (en) | 2002-02-21 | 2004-05-18 | Honeywell International, Inc. | Instrumentation and control circuit having multiple, dissimilar sources for supplying warnings, indications, and controls and an integrated cabin pressure control system valve incorporating the same |
US20040139751A1 (en) * | 2003-01-22 | 2004-07-22 | Liu Guang Jun | Master-slave engine bleed flow sharing control method and system |
US6782701B2 (en) | 2003-01-22 | 2004-08-31 | Honeywell International Inc. | Master-slave engine bleed flow sharing control method and system |
US7536865B2 (en) | 2005-02-09 | 2009-05-26 | Honeywell International Inc. | Method and system for balancing bleed flows from gas turbine engines |
US20060174628A1 (en) * | 2005-02-09 | 2006-08-10 | Honeywell International Inc. | Method and system for balancing bleed flows from gas turbine engines |
US7586888B2 (en) | 2005-02-17 | 2009-09-08 | Mobitrum Corporation | Method and system for mesh network embedded devices |
US7630736B2 (en) | 2005-10-11 | 2009-12-08 | Mobitrum Corporation | Method and system for spatial data input, manipulation and distribution via an adaptive wireless transceiver |
US8298055B2 (en) * | 2006-01-12 | 2012-10-30 | Airbus Operations Gmbh | Process and system for controlling the pressure in an aircraft cabin |
US20090305622A1 (en) * | 2006-01-12 | 2009-12-10 | Airbus Deutschland Gmbh | Process and system for controlling the pressure in an aircraft cabin |
US8427979B1 (en) | 2006-07-27 | 2013-04-23 | Mobitrum Corporation | Method and system for dynamic information exchange on location aware mesh network devices |
USRE47894E1 (en) | 2006-07-27 | 2020-03-03 | Iii Holdings 2, Llc | Method and system for dynamic information exchange on location aware mesh network devices |
US8411590B2 (en) | 2006-07-27 | 2013-04-02 | Mobitrum Corporation | Mesh network remote control device |
US8305935B2 (en) | 2006-07-27 | 2012-11-06 | Mobitrum Corporation | Method and system for dynamic information exchange on location aware mesh network devices |
US8305936B2 (en) | 2006-07-27 | 2012-11-06 | Mobitrum Corporation | Method and system for dynamic information exchange on a mesh network in a vehicle |
US7801058B2 (en) | 2006-07-27 | 2010-09-21 | Mobitrum Corporation | Method and system for dynamic information exchange on mesh network devices |
GB2443964A (en) * | 2006-11-17 | 2008-05-21 | Boeing Co | An environmental control system for controlling the environment in a pressurised compartment |
US7778735B2 (en) | 2006-11-17 | 2010-08-17 | The Boeing Company | Environmental control system, method, and computer program product for controlling the interior environment of a pressurized compartment |
GB2443964B (en) * | 2006-11-17 | 2009-01-28 | Boeing Co | Environmental control system and a method for controlling the interior environment of a pressurized compartment |
US20080115837A1 (en) * | 2006-11-17 | 2008-05-22 | The Boeing Company | Environmental control system, method, and computer program product for controlling the interior environment of a pressurized compartment |
US20120003908A1 (en) * | 2008-11-21 | 2012-01-05 | Airbus Operations Gmbh | Method And System For Emergency Ventilation Of An Aircraft Cabin In The Case Of A Leak In The Area Of An Air Mixer |
US9266601B2 (en) * | 2008-11-21 | 2016-02-23 | Airbus Operations Gmbh | Method and system for emergency ventilation of an aircraft cabin in the case of a leak in the area of an air mixer |
US20100173575A1 (en) * | 2009-01-08 | 2010-07-08 | Darrell Horner | Multiple outflow valve cabin pressure control system |
US8864559B2 (en) | 2009-01-08 | 2014-10-21 | Honeywell International Inc. | Multiple outflow valve cabin pressure control system |
US20100233950A1 (en) * | 2009-03-10 | 2010-09-16 | Honeywell International Inc. | Aneroid replacement |
US8328606B2 (en) * | 2009-03-10 | 2012-12-11 | Honeywell International Inc. | Aneroid replacement |
Also Published As
Publication number | Publication date |
---|---|
EP0818388B1 (en) | 2001-09-19 |
DE59704642D1 (en) | 2001-10-25 |
EP0818388A1 (en) | 1998-01-14 |
DE19628395A1 (en) | 1998-01-15 |
DE19628395C2 (en) | 1998-06-04 |
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